Accession Number : ADA308306
Title : Navier-Stokes Computation of Shock Tube Exit Jet for Non-Ideal Blast Simulations.
Descriptive Note : Final rept.,
Corporate Author : ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
Personal Author(s) : Guidos, Bernard J. ; Schraml, Stephen J. ; Ota, Dale K.
PDF Url : ADA308306
Report Date : APR 1996
Pagination or Media Count : 48
Abstract : A computational fluid dynamics study of the exit jet of the U.S. Army Research Laboratory's 1.68-m diameter shock tube is presented. The shock tube exit jet provides a test environment in which to assess vehicle response to non-ideal blast. In the present study, time-accurate Navier-Stokes solutions are generated to simulate a shock tube exit jet test in which pressure probe measurements were obtained. The computational results are compared to the experimental data, as well as to analytical results and other empirical data. An examination is made of the jet flow field structure, and the computational accuracy and requirements are assessed.
Descriptors : *NUCLEAR WEAPONS, *SHOCK WAVES, *COMPUTATIONAL FLUID DYNAMICS, MATHEMATICAL MODELS, ALGORITHMS, COMPUTERIZED SIMULATION, TIME DEPENDENCE, DYNAMIC RESPONSE, RESOLUTION, BLAST WAVES, ACCURACY, BOUNDARY LAYER, TURBULENT FLOW, VORTICES, PRESSURE MEASUREMENT, FLOW FIELDS, BLAST LOADS, MACH NUMBER, ARMORED PERSONNEL CARRIERS, UNSTEADY FLOW, NAVIER STOKES EQUATIONS, VISCOUS FLOW, BLAST, PRESSURE DISTRIBUTION, JET FLOW, DYNAMIC PRESSURE, DETONATIONS, SHOCK TUBES.
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE